CN110822476A - Rectification air duct system based on single cubic curve - Google Patents
Rectification air duct system based on single cubic curve Download PDFInfo
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- CN110822476A CN110822476A CN201910970029.5A CN201910970029A CN110822476A CN 110822476 A CN110822476 A CN 110822476A CN 201910970029 A CN201910970029 A CN 201910970029A CN 110822476 A CN110822476 A CN 110822476A
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- 238000012360 testing method Methods 0.000 claims abstract description 38
- 230000008602 contraction Effects 0.000 claims abstract description 17
- 238000009792 diffusion process Methods 0.000 claims abstract description 7
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000000889 atomisation Methods 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 239000000126 substance Substances 0.000 claims description 2
- 230000001413 cellular effect Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000012546 transfer Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
Abstract
The invention discloses a rectification air duct system based on a single cubic curve, which comprises a fan, wherein an outlet of the fan is sequentially communicated with a diffusion section, a rectification section, a contraction section and a test section; the fan can negatively feed back to adjust the wind speed according to the test requirement, the expansion section comprises a bypass valve, the rectification section comprises cellular networks with different apertures, the contraction section contracts in a specific proportion, and different components can be replaced according to the test section. The rectification air duct system provided by the invention has the advantages of simple structure, low manufacturing cost, short test process period, low test cost and reliable test result.
Description
Technical Field
The invention belongs to the technical field of hydromechanics, and particularly relates to a rectification air duct system based on a cubic curve.
Background
In the prior art, ground test research on the phenomenon of wall collision and heat transfer of fuel jet of an aircraft engine is required. At present, the contraction section of the rectification air duct system usually adopts a linear type or a double-cubic type curved surface. The linear curved surface contraction section is simple to process, but the air speed at the upper edge of the cross section is high, the air speed at the center is low, and air flow with good consistency cannot be obtained. The bicubic curve contraction section is complex to process, the outlet smoothness is poor, and the flatness of the airflow is influenced to a certain degree. The calculation of the Vickers curve contraction section is complex and requires calculation such as square development.
Accordingly, it would be desirable to have a solution that overcomes or alleviates at least one of the problems of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a rectified duct system based on a cubic single curve that overcomes or at least alleviates at least one of the above-mentioned problems of the prior art.
The invention is realized by adopting the following technical scheme:
a rectification air duct system based on a single cubic curve comprises a fan, wherein an outlet of the fan is sequentially communicated with a diffusion section, a rectification section, a contraction section and a test section; wherein the content of the first and second substances,
the shape of the constriction is determined according to the following equation
Where y is the constriction width, y0Is the inlet width of the constriction, y1Is the constriction exit width, L is the constriction total length, and x is the constriction length.
The invention is further improved in that the fan comprises a frequency converter capable of adjusting the wind speed and a controller thereof.
The invention is further improved in that the fan is connected with the ground fixing device, and rubber is arranged between the fan and the ground fixing device.
A further development of the invention is that the diffuser section contains a bypass valve for regulating the wind speed and pressure in the test section.
A further development of the invention is that the rectifying section comprises three groups of honeycomb networks of different apertures, and the apertures decrease in succession in the direction of the gas flow.
The honeycomb net is further improved in that the honeycomb net is of a regular hexagon structure, and the honeycomb net is sequentially a first honeycomb net, a second honeycomb net and a third honeycomb net along the airflow direction.
The invention further improves that when the test section is used for a cross-wind jet atomization test, the test section comprises a nozzle, an observation chamber and a heating plate, wherein the nozzle is a direct-injection nozzle and is arranged at the top of the observation chamber and used for jetting jet flow into the observation chamber, and the heating plate is arranged below the outlet of the nozzle and used for heating the jet flow of the nozzle.
The invention has the following beneficial technical effects:
according to the rectifying air duct system based on the single cubic curve, the size of the inlet of the contraction section, the size of the outlet of the contraction section and the length of the contraction section are given, and a unique cubic polynomial curve with a simple form can be obtained. The curve can be obtained without complex calculation and is composed of a polynomial. And the curvature is completely continuous, the defects of the existing contraction curve can be overcome, and the air flow at the outlet is uniformly distributed. The invention simplifies the design flow and has good application effect.
Further, preferably, the honeycomb network is arranged into three groups, the honeycomb network is in a regular hexagon shape, and the aperture of each group of honeycomb network is sequentially reduced along the airflow direction.
Furthermore, a bypass valve is arranged in front of the diffusion section to adjust the wind speed and pressure in the test section.
Furthermore, cross wind jet flow tests, cross wind heat transfer tests and the like can be carried out in the test section according to requirements.
Drawings
FIG. 1 is a schematic structural view of a rectifying air duct system according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of an expansion section and a rectifying section provided in accordance with an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a crosswind jet atomization test section provided by an embodiment of the invention;
FIG. 4 is a schematic structural diagram of a crosswind jet heat transfer test section provided by an embodiment of the invention.
FIG. 5 shows the results of the test of the distribution of the wind velocity in the vertical direction in the outlet cross section of the example of the present invention, wherein FIGS. 5(a) and (b) show the results of the test at two different wind velocities.
Description of reference numerals:
10. a fan; 20. an expansion section; 21. a bypass valve; 30. a rectifying section; 31. a first cellular network; 32. a second cellular network; 33. a third cellular network; 40. a contraction section; 50. a test section; 51. a nozzle; 52. an observation room; 53. heating the plate.
Detailed Description
For a better understanding of the present invention, a rectified duct system according to embodiments of the present invention will be described in detail below with reference to the accompanying drawings, and it should be noted that these embodiments are not intended to limit the scope of the present disclosure.
Referring to fig. 1, 2 and 3, the rectification air duct system based on the single cubic curve provided by the invention includes a fan 10, a diffuser section 20, a rectifier section 30, a contraction section 40 and a test section 50, which are connected in sequence.
The fan 10 includes a variable frequency drive with adjustable wind speed and its control. And a buffer device such as rubber is arranged between the fan 10 and the ground fixing device, so that the influence of vibration on the test is reduced.
The diffuser section 20 contains a bypass valve that can regulate the wind speed and pressure within the test section. The bypass valve also ensures that the pressure in the air duct is not too large, and the test safety is ensured.
The rectifying section 30 comprises three sets of honeycomb networks of different apertures. The pore diameter of the honeycomb net is reduced along the airflow direction in sequence. The honeycomb net is in a regular hexagon structure. The honeycomb network is a first honeycomb network 31, a second honeycomb network 32 and a third honeycomb network 33 in sequence along the direction of the air flow.
The shape of the constriction 40 is determined according to the following equation
Where y is the constriction width, y0Is the inlet width of the constriction, y1Is the constriction exit width, L is the constriction total length, and x is the constriction length.
The test section 50 can be replaced by different structures according to requirements, such as a crosswind jet atomization test or a crosswind jet heat transfer test and the like. Fig. 3 is a structural diagram of a cross-wind jet atomization test, and a nozzle 51 is a direct-injection nozzle which is usually applied to an afterburner of an aircraft engine and can inject jet flow into an observation chamber 52 and is arranged at the top of the observation chamber 52. Fig. 4 is a structural diagram of a crosswind jet heat transfer test, and a heating plate 53 is arranged below the outlet of a nozzle 51 and can be set to a fixed temperature, so that the jet heat transfer phenomenon under crosswind conditions is researched.
The fan 10 is connected with the diffusion section 20, the diffusion section 20 is connected with the rectifying section 30, the rectifying section 30 is connected with the contraction section 40, and the contraction section 40 is connected with the test section 50 through flanges, so that different test requirements can be met by replacing the fan at the later stage.
The outlet of the fan 10, the diffusion section 20, the rectifying section 30, the contraction section 40 and the test section 50 are all rectangular in cross section, so that shape conversion is not needed, and flow loss is reduced.
FIG. 5 shows the results of the test of the distribution of the wind velocity in the vertical direction on the outlet cross section of the example of the present invention. The outlet of the wind tunnel is 0-55 mm. At different maximum wind speeds, the velocity profiles are almost similar. And the wind speed at the outlet is uniformly distributed.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (7)
1. A rectification air duct system based on a single cubic curve is characterized by comprising a fan (10), wherein an outlet of the fan (10) is sequentially communicated with a diffusion section (20), a rectification section (30), a contraction section (40) and a test section (50); wherein the content of the first and second substances,
the shape of the constriction (40) is determined according to the following equation
Where y is the constriction width, y0Is the inlet width of the constriction, y1Is the constriction exit width, L is the constriction total length, and x is the constriction length.
2. The rectenna system based on the cubic-shift curve as claimed in claim 1, wherein the wind turbine (10) comprises a frequency converter and its controller for adjusting the wind speed.
3. The rectifying air duct system based on the cubic curve of claim 1, wherein the fan (10) is connected with a ground fixing device, and rubber is arranged between the fan (10) and the ground fixing device.
4. The rectenna system based on the cubic single curve of claim 1, wherein the divergent section (20) comprises a bypass valve for regulating the wind speed and pressure in the test section (50).
5. The rectenna system based on the simple cubic curve as claimed in claim 1, wherein the rectenna section (30) comprises three sets of honeycomb networks with different apertures, and the apertures decrease sequentially along the air flow direction.
6. The rectenna system based on the cubic-curve as claimed in claim 5, wherein the honeycomb network is a regular hexagonal structure and the honeycomb network comprises a first honeycomb network (31), a second honeycomb network (32) and a third honeycomb network (33) in sequence along the airflow direction.
7. The flow rectification air duct system based on the single cubic curve is characterized in that the test section (50) comprises a nozzle (51), an observation chamber (52) and a heating plate (53) when used for the cross wind jet atomization test, wherein the nozzle (51) is a direct-injection nozzle and is arranged at the top of the observation chamber (52) and used for injecting jet flow into the observation chamber (52), and the heating plate (53) is arranged below the outlet of the nozzle (51) and used for heating the jet flow of the nozzle (51).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910970029.5A CN110822476A (en) | 2019-10-12 | 2019-10-12 | Rectification air duct system based on single cubic curve |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910970029.5A CN110822476A (en) | 2019-10-12 | 2019-10-12 | Rectification air duct system based on single cubic curve |
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| CN110822476A true CN110822476A (en) | 2020-02-21 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115560357A (en) * | 2021-07-01 | 2023-01-03 | 中国航发商用航空发动机有限责任公司 | Rectifying device for combustion chamber air inlet test |
| CN115560357B (en) * | 2021-07-01 | 2024-04-30 | 中国航发商用航空发动机有限责任公司 | Rectifying device for combustion chamber air inlet test |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0518795A (en) * | 1991-07-15 | 1993-01-26 | Hitachi Ltd | Flow straightening duct and gas flow measuring device |
| KR20060003629A (en) * | 2004-07-07 | 2006-01-11 | 건국대학교 산학협력단 | Supersonic wind tunnel for education |
| CN104316286A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Low-turbulence design method of rotor wing pneumatic testing stand |
| CN205211269U (en) * | 2015-12-29 | 2016-05-04 | 厦门大学 | Teaching is with backward flow and dual -purpose small -size low -speed smoke wind tunnel of direct current |
| CN108709712A (en) * | 2018-07-31 | 2018-10-26 | 大连凌海华威科技服务有限责任公司 | Subsonic jets formula air feeders calibration wind tunnel |
| CN109696288A (en) * | 2018-12-03 | 2019-04-30 | 中国辐射防护研究院 | A kind of simulation tests in environment wind tunnel device and its experiment detection method |
| CN210717656U (en) * | 2019-10-12 | 2020-06-09 | 西安交通大学 | Rectification air duct system based on single cubic curve |
-
2019
- 2019-10-12 CN CN201910970029.5A patent/CN110822476A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0518795A (en) * | 1991-07-15 | 1993-01-26 | Hitachi Ltd | Flow straightening duct and gas flow measuring device |
| KR20060003629A (en) * | 2004-07-07 | 2006-01-11 | 건국대학교 산학협력단 | Supersonic wind tunnel for education |
| CN104316286A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Low-turbulence design method of rotor wing pneumatic testing stand |
| CN205211269U (en) * | 2015-12-29 | 2016-05-04 | 厦门大学 | Teaching is with backward flow and dual -purpose small -size low -speed smoke wind tunnel of direct current |
| CN108709712A (en) * | 2018-07-31 | 2018-10-26 | 大连凌海华威科技服务有限责任公司 | Subsonic jets formula air feeders calibration wind tunnel |
| CN109696288A (en) * | 2018-12-03 | 2019-04-30 | 中国辐射防护研究院 | A kind of simulation tests in environment wind tunnel device and its experiment detection method |
| CN210717656U (en) * | 2019-10-12 | 2020-06-09 | 西安交通大学 | Rectification air duct system based on single cubic curve |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115560357A (en) * | 2021-07-01 | 2023-01-03 | 中国航发商用航空发动机有限责任公司 | Rectifying device for combustion chamber air inlet test |
| CN115560357B (en) * | 2021-07-01 | 2024-04-30 | 中国航发商用航空发动机有限责任公司 | Rectifying device for combustion chamber air inlet test |
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